US9769431B2 - Ice detector - Google Patents

Ice detector Download PDF

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Publication number
US9769431B2
US9769431B2 US14/406,769 US201314406769A US9769431B2 US 9769431 B2 US9769431 B2 US 9769431B2 US 201314406769 A US201314406769 A US 201314406769A US 9769431 B2 US9769431 B2 US 9769431B2
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Prior art keywords
icing
ice
rod
image
icing rod
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US14/406,769
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US20150163460A1 (en
Inventor
Xianlin Shi
Guopeng Nan
Geping Li
Xudong Xin
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Shanghai Aircraft Design And Research Institute
Commercial Aircraft Corp of China Ltd
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Shanghai Aircraft Design And Research Institute
Commercial Aircraft Corp of China Ltd
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Assigned to COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE, Commercial Aircraft Corporation of China, Ltd. reassignment COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LI, Geping, NAN, Guopeng, SHI, Xianlin, XIN, XUDONG
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N7/00—Television systems
    • H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
    • H04N7/183—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/20—Means for detecting icing or initiating de-icing
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T7/00—Image analysis
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T7/00—Image analysis
    • G06T7/90—Determination of colour characteristics
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
    • H04N23/50—Constructional details
    • H04N23/51—Housings
    • H04N5/2252—

Definitions

  • the present invention relates to the field of ice detection, and particularly to flight ice detecting device for detecting icing condition.
  • the flight ice detection which can provide ice alert information for pilots to activate anti-ice system or auto-activate ant-ice system.
  • the ice detection system is an important improvement for flight safety.
  • U.S. Pat. No. 4,553,137 discloses an ice detector based on a vibrating principle of magnetostrictive material.
  • a probe of the ice detector is made of magnetostrictive material.
  • This type of ice detector is extensively applied to aircraft such as A340, A380, B747, B777, ERJ-190, CRJ200 and ARJ.
  • U.S. Pat. No. 7,104,502 also discloses an ice detector based on a vibrating principle of magnetostrictive material, which can improve ice detection performance at near freezing conditions by changing the supporting shape of the ice detector in U.S. Pat. No. 4,553,137.
  • U.S. Pat. No. 7,370,525 discloses a photoelectrical ice detector.
  • U.S. Pat. No. 4,461,178 discloses an ultrasonic wave ice detector.
  • U.S. Pat. No. 5,748,091 discloses a fiber optic ice detector.
  • the critical temperature of ice detector is higher than that of the front edge of wing/nacelle.
  • the critical temperature difference can result in the ice accretion on the edge of wing/nacelle prior to the ice detector.
  • an object of the present invention is to provide an ice detector based on image processing technology which can eliminate the critical temperature difference.
  • an ice detector comprising:
  • an icing assembly comprising an icing rod having an ice accretion surface and a support structure, wherein the icing rod is transparent and an illuminating element is disposed therein; at least one visual sensor configured to obtain an image of the ice accretion surface; a controller electrically connected to the visual sensor and comprising an image contrast module configured to compare the image obtained from the visual sensor with an initial image of the ice accretion surface so as to judge whether ice is formed on the ice accretion surface of the icing rod; wherein, the icing assembly comprises a refrigerating element respectively connected to the icing rod and the support structure.
  • arranging the refrigerating element on the icing rod assembly to perform active refrigeration for the icing rod may reduce the surface temperature of the icing rod and facilitate ice accretion on the icing rod before ice is formed on the wing/nacelle.
  • the refrigerating element is a semiconductor refrigerating element which cold end is connected to the icing rod to perform active refrigeration for the icing rod, and which hot end is connected to the support structure and dissipates heat via it.
  • the semiconductor refrigerating element is disposed at a lower end of the icing rod, and the cold end is above the hot end.
  • the icing assembly may further be configured as follows: the icing rod has a first inner cavity, and the semiconductor refrigerating element is disposed in the first inner cavity of the icing rod; the semiconductor refrigerating element has a second inner cavity and an upper end of the support structure extends into the second inner cavity; the cold end of the semiconductor refrigerating element is outside and the hot end is inside.
  • the icing rod is constructed as a streamlined wing-shaped structure.
  • the ice accretion surface has a smaller pressure coefficient.
  • the smaller pressure coefficient means a lower surface temperature and a higher critical temperature. It facilitates the ice accretion on the icing rod before ice is formed on the wing/nacelle.
  • the lateral side of the icing rod is configured to be wavy in a chordwise direction to facilitate water collection.
  • the icing rod has a sufficient length in a chordwise direction to ensure that supercooled large water droplets, in the event of break, splashing or the like, can freeze on the lateral side of the icing rod. This enables the ice detector of the present invention to have an ability to detect supercooled large water droplets so that the use scope of the ice detector of the present invention is expanded.
  • a front edge of the icing rod is configured to be cylindrical or wing-shaped.
  • a curvature of the front edge of the icing rod is small enough to allow a water-collection coefficient of the icing rod to top 0.9.
  • one of the at least one visual sensor is arranged exactly opposed to the ice accretion surface, and the other of the at least one visual sensor is arranged laterally opposed to the ice accretion surface.
  • the positions of the icing rod and the visual sensor are arranged in a coordinated manner to better obtain the ice image of the icing rod.
  • the visual sensor is a miniature camera device.
  • each of the at least one visual sensor at least comprises a lens and an image sensor, wherein the lens is used to obtain the image of the ice accretion surface, and the image sensor is electrically connected to and transmits the image to the image contrast module of the control unit.
  • the ice detector further comprises a flange plate connected between the icing assembly and the controller.
  • the ice detector is mounted on an aircraft via the flange plate.
  • a recessed chamber with a transparent window is provided on the flange plate, and the lens of the visual sensor is exposed in the recessed chamber.
  • the recessed chamber is provided on the flange plate such that the lens of the visual sensor is exactly opposed to and/or laterally opposed to the ice accretion surface of the icing rod and the transparent window provides protection for the lens and prevents the lens from mist.
  • the recessed chamber has a slant surface facing towards the icing assembly, and the lens is exposed from the slant surface.
  • the arrangement of the slant surface provides convenience and greater flexibility for the arrangement of the visual sensor relative to the icing rod.
  • the slant surface of the recessed chamber is provided with an automatically adjustable illuminating element, and/or the visual sensor itself carries an illuminating element such as an automatically adjustable flash lamp.
  • the arrangement of the illuminating elements helps the visual sensor to better obtain the image of the ice accretion surface under different light intensity conditions.
  • the icing rod is provided with an electrical heater for deicing, and the electrical heater is used to remove accumulated ice from the icing rod after ice is detected, and then ice detection enters next cycle of ice accretion-detecting ice-heating to remove ice-cooling and cooling.
  • the transparent window is provided with an anti-ice electrical heater.
  • the arrangement of the electrical heater assists in keeping an inner surface of the transparent window from mist and keeping an outer surface from icing, and on the one hand, ensures that the transparent window remains transparent so that the visual sensor effectively obtains true icing conditions of the ice accretion surface, and on the other hand ensures that air in the recessed chamber is higher than a dew point temperature, thereby effectively preventing mist forming on the lens surface.
  • the controller further comprises a heating control module which is electrically connected to the image contrast module and used to control the electrical heaters to perform electrical heating.
  • the illuminating element is disposed in the icing rod to better outline the shape of ice and cooperate with the visual sensor to obtain images of the icing rod under different light intensities and improve reliability of ice detection.
  • the illuminating element comprises two sets of illuminating elements which are respectively disposed at a front edge and a middle-rear portion of the transparent icing rod.
  • the ice accretion surface of the icing rod is provided with color marks facilitating color identification, which help better outline the shape of the ice.
  • FIG. 1 illustrates an isometric diagram of an ice detector according to a preferred embodiment of the present invention
  • FIG. 2 is a top plane view of the ice detector of FIG. 1 , wherein an arrow indicates an air stream direction;
  • FIG. 3 is a sectional view taken along line A-A of the ice detector of FIG. 2 , wherein an arrow indicates an air stream direction;
  • FIG. 4 is a partial enlarged view of portion B of the ice detector of FIG. 2 ;
  • FIG. 5A illustrates a cross-sectional view of a first embodiment of an icing rod of the ice detector of FIG. 1 , wherein an arrow indicates an air stream direction;
  • FIG. 5B illustrates a cross-sectional view of a second embodiment of an icing rod of the ice detector of FIG. 1 , wherein an arrow indicates an air stream direction;
  • FIG. 6 illustrates a block diagram of functional modules of the ice detector according to a preferred embodiment of the present invention
  • FIG. 7 illustrates a schematic diagram showing working principles of ice detection of the ice detector according to a preferred embodiment of the present invention, wherein ice detection is cyclically performed in a way of icing-detecting ice-heating to remove ice-cooling;
  • FIG. 8A illustrates an isometric diagram of a preferred embodiment of an icing assembly of the ice detector of FIG. 1 , wherein a semiconductor refrigerating element is arranged between an icing rod and a support structure in a longitudinal direction;
  • FIG. 8B illustrates a top planar view of the icing assembly of FIG. 8A ;
  • FIG. 8C illustrates a sectional view taken along line A-A of the icing assembly of FIG. 8B ;
  • FIG. 8D illustrates a partial enlarged view of portion B of the icing assembly of FIG. 8C ;
  • FIG. 9A illustrates an isometric diagram of another preferred embodiment of an icing assembly of the ice detector of FIG. 1 , wherein a semiconductor refrigerating element is arranged between an icing rod and a support structure in an in-out direction along the circumference;
  • FIG. 9B illustrates a top planar view of the icing assembly of FIG. 9A ;
  • FIG. 9C illustrates a sectional view taken along line A-A of the icing assembly of FIG. 9B ;
  • FIG. 10A illustrates a longitudinal sectional view of a third embodiment of an icing assembly of the ice detector of FIG. 1 , wherein an arrow indicates an air stream direction;
  • FIG. 10B is a sectional view taken along line D-D of the icing assembly of FIG. 10A .
  • icing condition in the text should be understood as icing conditions and supercooled large droplet icing conditions defined by Appendix C of Chinese Civil Aviation Regulations Part 25, “transport category aircraft airworthiness standards” (CCAR-25).
  • water in the text should be understood as supercooled droplet under icing condition.
  • FIGS. 1-4 An ice detector according to a preferred embodiment of the present invention is shown in FIGS. 1-4 .
  • the ice detector 100 comprises: an icing assembly 1 , a visual sensor 31 and a controller 5 .
  • the icing assembly 1 comprises an icing rod 11 and a support rod 12 supporting the icing rod 11 and enabling it to extend into air stream and serving as a support structure.
  • the icing rod 11 has an ice accretion surface 110 on an outside wall thereof.
  • the visual sensor 31 is arranged exactly opposed to a front edge 111 of the icing rod 11 to obtain an image of the ice accretion surface 110 .
  • the visual sensor 31 comprises a lens 310 and an image sensor (CCD or CMOS) 311 (see FIG. 6 ).
  • the controller 5 is configured to be electrically connected to the visual sensor 31 and comprises an image contrast module 510 (see FIG. 6 ) to compare the image from the visual sensor 31 with an initial image of the ice accretion surface 110 .
  • the ice detector 100 preferably has a flange plate 7 by which the ice detector is mounted on the aircraft.
  • the flange plate 7 is mounted between the icing assembly 1 and the controller 5 to support the icing assembly 1 on the one hand and to mount the visual sensor 31 on the other hand.
  • a recessed chamber 71 with a transparent window 710 is provided on the flange plate 7 , and the lens 310 of the visual sensor 31 is exposed in the recessed chamber 71 .
  • the recessed chamber is provided on the flange plate such that the lens 310 of the visual sensor 31 is exactly opposed to the ice accretion surface of the front edge 112 of the icing rod and the transparent window 710 provides protection for the lens.
  • the arrangement of the slant surface provides convenience for the arrangement of the visual sensor relative to the icing rod.
  • an automatically adjustable illuminating element 712 is provided on the slant surface 711 of the recessed chamber 71 .
  • the visual sensor 31 itself may also carry an illuminating element such as an automatically adjustable flash lamp.
  • the illuminating element helps the visual sensor 31 to better obtain an image from the ice accretion surface 110 .
  • the slant surface 711 of the recessed chamber 71 is further provided with a light measuring element 713 electrically connected to the illuminating element 712 to sense light brightness in the surrounding environment and trigger the illuminating element 712 to work when needed.
  • the second visual sensor 32 disposed laterally opposed to the ice accretion surface 110 of the icing rod 11 , i.e., exactly opposed to the ice accretion surface of a lateral side 114 of the icing rod.
  • the second visual sensor 32 comprises a second lens 320 and a second image sensor 321 (see FIG. 6 ).
  • the second lens 320 is located in a second recessed chamber 72 of the flange plate 7 and exposed to obtain an image of the ice accretion surface 110 , wherein the second recessed chamber 72 having a second transparent window 720 is angled relative to the first recessed chamber 71 at substantially a 90° angle, i.e., the second recessed chamber 72 is located relative to a lateral side of the icing rod 11 so that the second lens 320 laterally faces the ice accretion surface 110 .
  • the second recessed chamber 72 has a second slant surface 721 on which are provided a second automatically adjustable illuminating element 722 and a second light measuring element 723 electrically connected to the second illuminating element 722 .
  • the icing rod 11 is preferably provided with an electrical heater (not shown) for deicing, and meanwhile the transparent windows 710 , 720 are preferably provided with an electrical heater (not shown) for preventing ice.
  • the controller 5 preferably further comprises a heating control module 520 which is electrically connected to the image contrast module 510 and used to control the electrical heaters on the icing rod and the transparent windows to perform electrical heating.
  • image sensors 310 , 320 of the visual sensor 31 and the second visual sensor 32 may preferably be located in a housing of the controller 5 .
  • Integral parts and their functions in the present preferred embodiment are respectively introduced below with reference to FIGS. 1-4 and FIG. 6 .
  • the visual sensors 31 , 32 may be miniature camera devices which shoot, at a certain frequency, images of the ice accretion surface 110 of the icing rod 11 under different light intensities.
  • Light measuring elements 713 , 723 measure different light intensities of the external (namely, ambient environment) and may be photosensitive resistors.
  • Illuminating elements 712 , 722 provide illumination for the icing rod 11 and may be automatically adjustable flash lamps or automatically adjustable illuminating elements. Under control of the image sensors 311 , 321 , the illuminating elements provide different illumination intensities according to different light intensities of the external.
  • Image sensors (CCD or CMOS) 311 , 321 adjust illumination intensity and lens shutter according to the light intensity measured by the light measuring elements 713 , 723 to obtain the images of the icing rod.
  • Lenses 310 , 320 employ a fixed focal lens which depth of field can cover the whole icing rod 11 .
  • Transparent windows 710 , 720 with an electrical heater perform electrical heating under control of the heating control module 520 to ensure that the transparent window surface away from ice or mist and ensure that the light measuring elements 713 and 723 , lenses 310 , 320 and illuminating elements 712 , 722 have a clear field of vision.
  • the light measuring elements 713 and 723 may be disposed in the lenses or in the illuminating elements 712 , 722 .
  • the Icing Assembly 1 is :
  • the icing rod 11 with an electrical heater has a streamlined wing-shaped structure and has a smaller pressure coefficient (higher critical temperature) and larger water-collection coefficient.
  • the support structure 12 with an electrical heater has a length which guarantees a water droplet shield area of the icing rod 11 .
  • the ice accretion surface of the icing rod 11 may be provided with marks as characteristic points for image contrast; color of the ice accretion surface 110 of the icing rod, color of the marks and color of the illumination light should be in a large contrast, for example, the color of the ice accretion surface uses green, the color of the marks uses red and the illumination lamp uses blue, which better outlines a shape of ice.
  • a material of the icing assembly 1 is not particularly limited.
  • the icing rod 11 is designed streamlined, a curvature of the front edge 112 of the icing rod is designed smaller enough to ensure that a water-collection coefficient obtained by the icing rod tops 0.9, and the streamlines shape may ensure that the icing rod 11 obtains a smaller pressure coefficient (higher critical temperature); besides, the icing rod 11 is designed to have a sufficient length in a chordwise direction to ensure that supercooled large water droplets, in the event of break, splashing or the like, gradually release latent heat and then freeze on the ice accretion surface 110 .
  • the front edge 112 of the icing rod is designed cylindrical, as shown in FIGS. 5A and 5B .
  • the lateral side 114 of the icing rod is configured to be wavy in a chordwise direction (indicated by the arrows depicted in FIGS. 5A and 5B ) as shown in FIG. 5B to facilitate water collection.
  • the Image Contrast Module 510 The Image Contrast Module 510 :
  • the image contrast module 510 compares the icing rod image obtained from the image sensor 311 , 321 with the icing rod image without ice stored in a memory by using an area characteristic method (shape). If the two images have a similarity lower than a threshold value, it is judged that ice is formed, an electrical interface (namely, an electrical connector) 8 is coordinated to send an icing signal which is transmitted to an aircraft-related system 9 .
  • an electrical interface namely, an electrical connector
  • An image contrast procedure is mature technology and applied to aspects such as human image identification or entrance guard system, so it is not detailed any longer here.
  • the above controller 5 may further comprise a self-check module (not shown) which is responsible for performing BIT (self-check) for the ice detector. If a component fails, an electrical connector 8 is coordinated to send a fault signal which is transmitted to an aircraft-related system 9 .
  • the self-check function is mature technology and is not detailed any longer here.
  • the electrical connector 8 is connected to an aircraft power source and outputs icing and fault signals generated by the visual detectors 31 , 32 ; an interior of the controller 5 is connected to the image sensor 311 , 321 via a bus interface. When real-time similarity value and icing rod images need to be obtained upon test flight, it is connected to a data collecting apparatus via the bus interface.
  • the electric connector is mature technology and is not detailed any longer here.
  • the lenses 310 , 320 of the visual sensors 31 , 32 shoot, at a certain frequency, images of the ice accretion surface of the front side and lateral side of the icing rod 11 ; the image contrast module 510 compares the icing rod image in presence of ice obtained from the image sensors 311 , 321 with the icing rod image without ice stored in a memory to determine image similarity based on area characteristic algorithm.
  • the electrical connector 8 is coordinated to send an icing signal for use by the aircraft user system 9 .
  • the heating control module 520 performs electrical heating for the icing rod 11 and the support rod 12 .
  • ice detection enters next cycle of ice accretion on the icing rod-detecting ice-heating to remove ice-cooling of the icing rod; the heating control module 520 , with a certain power, heats the transparent windows 710 , 720 to prevent the transparent windows from ice and/or mist; the self-check module performs BIT for respective parts, the controller 5 and the electrical connector 8 , and in event of a fault, sends a fault signal which will be recorded and processed by the aircraft user system 9 .
  • Arranging the refrigerating element on the icing rod assembly (described more fully below) to perform active refrigeration for the icing rod may further reduce the surface temperature of the icing rod and facilitate ice accretion on the icing rod before ice is formed on the wing/nacelles.
  • the outer shape may be optimized through aerodynamic analysis and droplet impingement analysis to make it have a smaller pressure coefficient and a larger water collection coefficient;
  • the smaller pressure coefficient means that the icing rod has a lower surface temperature and a higher critical temperature and is more liable to ice accretion;
  • the larger water collection coefficient means a larger amount of ice accretion in a per unit time; it facilitates ice accretion on the icing rod before ice is formed on the wing/nacelles.
  • the icing rod has a sufficient length in a chordwise direction to ensure that supercooled large water droplets, in the event of break, splashing or the like, freeze on the side of the icing rod, that is to say, the ice detector of the present invention has an ability to detect supercooled large water droplets so that the use scope of the ice detector of the present invention is expanded.
  • the material of the icing rod may be metal or other materials; the positions of the icing rod and the visual sensor are arranged in a coordinated manner to better obtain the ice image of the icing rod; besides, the material, shape and arrangement manner of the probe in the present invention exhibit larger flexibility.
  • Step S 1 the image sensor 311 and image sensor 321 , at a certain frequency for example once 1 second, measure light intensity via the light measuring elements 713 , 723 , control the light illuminating elements 712 , 722 and the lenses 310 , 320 , and meanwhile shoot images of the ice accretion surface 110 of the front side and lateral side of the icing rod 11 ;
  • Step S 2 the image contrast procedure goes as follows: comparing the shot images of the front side and lateral side of the icing rod with images of the front side and lateral side of the icing rod without ice stored in a memory by using area characteristic algorithm.
  • a threshold e.g. 20%
  • icing is judged and an icing signal lasting a certain time period for example 60 seconds will be sent;
  • Step S 3 after obtaining the icing signal, the heating control module 520 begins to perform electrical heating for the icing rod 11 and the support rod 12 to remove ice; after the icing rod cools, ice begins to be formed again; if icing is detected again within 60 seconds, the icing signal will last another 60 seconds, and steps S 1 and S 2 are repeated.
  • Step S 4 the heating control module 520 constantly performs electrical heating for the transparent windows 710 , 720 to prevent ice accretion to keep the transparent windows transparent.
  • the icing assembly further preferably comprises a semiconductor refrigerating element.
  • the icing assembly 1 ′ in a preferred embodiment comprises an icing rod 11 ′, a support rod 12 ′ and a semiconductor refrigerating element 13 ′, wherein the semiconductor refrigerating element 13 ′ is longitudinally disposed between the icing rod 11 ′ and the support rod 12 ′.
  • the semiconductor refrigerating element 13 ′ is longitudinally disposed between the icing rod 11 ′ and the support rod 12 ′.
  • a cold end 131 ′ of the semiconductor refrigerating element 13 ′ is connected to the icing rod 11 ′ to perform active refrigeration for the icing rod 11 ′, and a hot end 133 ′ is connected to the support rod 12 ′ and dissipates heat via the support rod 12 ′.
  • the semiconductor refrigerating element 13 ′ cools the icing rod 11 ′ ⁇ T° C. temperature (generally 1-2° C.), i.e., the temperature of the icing rod decreases by ⁇ T° C. as compared with an ambient temperature.
  • arranging the semiconductor refrigerating element on the icing rod assembly to perform active refrigeration for the icing rod may further reduce the surface temperature of the icing rod and facilitate ice accretion on the icing rod before ice is formed on the wing/nacelles so that the ice detector detects ice accretion before ice is formed on the wing/nacelle such that subsequent countermeasures are taken.
  • FIGS. 9A-9C illustrate another preferred embodiment of the icing assembly, wherein the semiconductor refrigerating element is arranged between the icing rod and the support structure in an in-out direction along the circumference.
  • the semiconductor refrigerating element 13 ′′ may be made in a shape of a concentric elliptical ring, its periphery is a cold end 131 ′′ connected to the icing rod 11 ′′, and its interior is a hot end 133 ′′ connected to the support 12 ′′. Heat may be transferred from an upper half of the support rod 12 ′′ to its lower half, and then dissipated.
  • the icing rod 11 ′′ has a first inner cavity 112 ′′
  • the semiconductor refrigerating element 13 ′′ is disposed in the first inner cavity 112 ′′ of the icing rod 11 ′′
  • the semiconductor refrigerating element 13 ′′ has a second inner cavity 132 ′′ and an upper end of the support rod 12 ′′ extends into the second inner cavity 132 ′′
  • the cold end 131 ′′ of the semiconductor refrigerating element is outside and the hot end 133 ′′ is inside.
  • the semiconductor refrigerating element itself is based on Peltier principle, and is mature application and not detailed any longer here.
  • FIG. 10 OA and FIG. 10B illustrate a further preferred embodiment of the icing assembly.
  • the icing rod 11 ′′′ carries an electrical heater and is transparent, e.g., the transparent icing rod with an electrical heater is made of transparent glass (or other transparent material) with an electrical heater, and two sets of illuminating elements, namely, a third illuminating element 141 ′′′ and a fourth illuminating element 143 ′′′, are preferably disposed therein, wherein the third illuminating element 141 ′′′ mainly provides illumination for the front edge of the icing rod, and the fourth illuminating element 143 ′′′ provides illumination for a middle portion and a rear portion of the icing rod.
  • Provision of the illuminating elements in the icing rod 11 ′′′ can better outline the shape of ice to cooperate with the visual sensor to obtain images of the icing rod under different light intensities. Additionally, it should be appreciated that after measuring the light intensity, the light measuring elements 713 , 723 in the above preferred embodiments of the present invention controls the two sets of illuminating elements in the icing rod 11 ′′′ to better obtain the images of the ice accretion surface on the front side and the lateral side of the icing rod 11 ′′′.
  • the icing assembly shown in FIG. 8A - FIG. 8D may completely employ the icing rod structure shown in FIG. 10A - FIG. 10B , i.e., the icing rod of the icing assembly shown in FIGS. 8A-8D is also made of a transparent material, and illuminating elements are disposed therein. Certainly, illuminating elements may also be disposed in the icing rod shown in FIG. 9A - FIG. 9C if needed. Besides, regarding the streamlined wing-shaped structure of the icing rod, namely, the icing rod configuration as shown in FIG. 5A and FIG. 5B , it is suitable in the icing assembly in any one of the above preferred embodiments.
US14/406,769 2012-12-04 2013-12-03 Ice detector Active 2034-11-05 US9769431B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CN201210513790 2012-12-04
CN201210513790.4A CN103101626B (zh) 2012-12-04 2012-12-04 结冰探测器
CN201210513790.4 2012-12-04
PCT/CN2013/088419 WO2014086276A1 (fr) 2012-12-04 2013-12-03 Détecteur de givre

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US9769431B2 true US9769431B2 (en) 2017-09-19

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EP (1) EP2876050B1 (fr)
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US20220299675A1 (en) * 2021-03-19 2022-09-22 Subaru Corporation Icing detector
US20220380057A1 (en) * 2021-05-25 2022-12-01 Airbus Operations Sas Device for measuring the thickness of an accretion of ice on a surface and aircraft provided with such a device

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Publication number Priority date Publication date Assignee Title
CN103101626B (zh) * 2012-12-04 2015-09-02 中国商用飞机有限责任公司 结冰探测器
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